CN106864773B - A kind of instrument cabin structure of vehicle - Google Patents
A kind of instrument cabin structure of vehicle Download PDFInfo
- Publication number
- CN106864773B CN106864773B CN201710210857.XA CN201710210857A CN106864773B CN 106864773 B CN106864773 B CN 106864773B CN 201710210857 A CN201710210857 A CN 201710210857A CN 106864773 B CN106864773 B CN 106864773B
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- Prior art keywords
- instrument
- instrument room
- room shell
- jet pipe
- end frame
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- 238000009434 installation Methods 0.000 claims abstract description 40
- 238000005422 blasting Methods 0.000 claims abstract description 11
- 238000010146 3D printing Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 4
- 238000010276 construction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention discloses a kind of instrument cabin structures of vehicle, including instrument room shell, the outside of instrument room shell is equipped with covering, the top and bottom of instrument room shell are respectively equipped with upper end frame and lower end frame, several upper blasting bolt boxes and lower blasting bolt box are respectively equipped on the outside of the outside of upper end frame and lower end frame, several hinge seats are also associated on the outside of the frame of upper end, hinge hole is equipped on each hinge seat, the inside of instrument room shell is respectively equipped with interior road Duan Kuanghenei roads lower end frame, interior road end frame is connected by several supporting beams with instrument room shell, the upper end of supporting beam is equipped with instrument and installs version, Nei Lu lower ends frame is connected by stringer with instrument room shell, the lower end of instrument room shell is equipped with several big jet pipe installation interfaces, small jet pipe installation interface and gas cylinder installation position and bearing.Instrument cabin structure of the present invention alleviates the stability of weight holding structure on the premise of bearing requirements are ensured of structure while integrally improving shell section carrying capacity.
Description
Technical field
The present invention relates to vehicle instrument room technical field, it particularly relates to a kind of instrument cabin structure of vehicle.
Background technology
Common carrier rocket shell segment structure is a segment structure mostly, intermediate without the requirement of other design objectives, may only be realized
The requirement of carrying, it is not possible to which the installation of instrument and equipment and the bearing requirements of middle part are provided；In addition, in General Instrument cabin structure
Instrument and equipment is side hanging or cantilevered, therefore cannot meet the requirement to load environment condition, and with structure bulky
The shortcomings that.
The content of the invention
For the above-mentioned technical problem in correlation technique, the present invention proposes a kind of instrument cabin structure of vehicle, Neng Gouke
Take the above-mentioned deficiency of the prior art.
To realize above-mentioned technical purpose, the technical proposal of the invention is realized in this way：
A kind of instrument cabin structure of vehicle, including instrument room shell, the outside of the instrument room shell is equipped with covering, institute
The top and bottom for stating instrument room shell are respectively equipped with upper end frame and lower end frame, the outside of the upper end frame and the outside of lower end frame
Several upper blasting bolt boxes and lower blasting bolt box are respectively equipped with, several hinge seats, institute are also associated on the outside of the upper end frame
It states and hinge hole is equipped on each hinge seat, the inside of the instrument room shell is respectively equipped with interior road Duan Kuanghenei roads lower end
Frame, the interior road end frame are connected by several supporting beams with instrument room shell, and the upper end of the supporting beam is installed equipped with instrument
Plate, Nei Lu lower ends frame are connected by stringer with instrument room shell, and the lower end of the instrument room shell is equipped with several big sprays
Pipe installation interface, small jet pipe installation interface and gas cylinder installation position and bearing.
Further, the supporting beam shares eight, is trapezoidal supporting beam.
Preferably, several lightening holes are equipped in each supporting beam.
Further, big jet pipe installation interface and small jet pipe installation interface share 20, respectively along instrument room shell
Axially, radially and tangentially set.
Further, the big jet pipe installation interface and small jet pipe installation interface by aluminum alloy forge piece and instrument room outside
Stringer, covering or the lower end frame of shell are connected.
Further, big jet pipe installation interface and small jet pipe installation interface are molded using titanium alloy 3D printing.
Further, each described hinge seat includes 2 hinge plates being separated by, and is equipped with hinge on each hinge plate
Hole.
Beneficial effects of the present invention：Instrument room shell mechanism is whole to improve shell using covering, stringer semi-monocoque construction form
The weight of structure is alleviated while section carrying capacity；Centre is using trapezoidal backbar support structure support engine and satellite
Load weight, the stability of holding structure on the premise of bearing requirements are ensured.
Description of the drawings
It in order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is a kind of structure diagram of the instrument cabin structure of the vehicle described according to embodiments of the present invention；
Fig. 2 is a kind of structure diagram of the instrument room structure bottom point of vehicle described in the embodiment of the present invention；
In figure：1st, covering；2nd, upper end frame；3rd, lower end frame；4th, interior road end frame；5th, upper blasting bolt box；6th, lower explosion spiral shell
Bolt box；7th, Nei Lu lower ends frame；8th, hinge seat；9th, stringer；10th, small jet pipe installation interface；11st, bearing；12nd, big jet pipe installation connects
Mouthful；13rd, gas cylinder installation position；14th, supporting beam.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art's all other embodiments obtained belong to what the present invention protected
Scope.
As shown in Figs. 1-2, the instrument cabin structure of a kind of vehicle according to embodiments of the present invention, including instrument room outside
Shell, the outside of the instrument room shell are equipped with covering 1, and the top and bottom of the instrument room shell are respectively equipped with 2 He of upper end frame
Lower end frame 3, the outside of the upper end frame 2 and the outside of lower end frame 3 are respectively equipped with several upper blasting bolt boxes 5 and lower blasting bolt
Box 6 is also associated with several hinge seats 8 on the outside of the upper end frame, hinge hole is equipped on each described hinge seat 8, described
The inside of instrument room shell is respectively equipped with interior road end frame 4 and Nei Lu lower ends frame 7, and the interior road end frame 4 passes through several supports
Beam 14 is connected with instrument room shell, and the upper end of the supporting beam is equipped with instrument installing plate, and Nei Lu lower ends frame 7 passes through stringer 9
It is connected with instrument room shell, the lower end of the instrument room shell connects equipped with several big jet pipe installation interfaces 12, the installation of small jet pipe
Mouth 10, gas cylinder installation position 13 and bearing 11.
In one embodiment, the supporting beam 14 shares eight, is trapezoidal supporting beam.
In one embodiment, several lightening holes are equipped in each supporting beam 14.
In one embodiment, big jet pipe installation interface 12 and small jet pipe installation interface 10 share 20, respectively edge
The axial direction of instrument room shell is radially and tangentially set.In one embodiment, the big jet pipe installation interface 12 and small jet pipe
Installation interface 10 is connected by aluminum alloy forge piece with the stringer 9, covering 1 or lower end frame 3 of instrument room shell.
In one embodiment, big jet pipe installation interface 12 and small jet pipe installation interface 10 use titanium alloy
3D printing is molded.
In one embodiment, each described hinge seat 8 includes 2 hinge plates being separated by, and on each hinge plate
It is equipped with hinge hole.
In order to facilitate understand the present invention above-mentioned technical proposal, below by way of in specifically used mode to the present invention it is above-mentioned
Technical solution is described in detail.
When specifically used, a kind of vehicle instrument cabin structure according to the present invention, covering 1 is carried in overall structure
During play the role of antitorque and increase stability, upper end frame 2 and lower end frame 3 be distributed with blasting bolt box 5 and under
Blasting bolt box 6 and hinge seat 8 play the role of and rocket other section structures connection and separated；Stringer 9 is instrument room knot
The main load bearing component of structure, assumes responsibility in structure about 90% load, and interior road end frame 4 and Nei Lu lower ends frame 7 form instrument room
The interior road carrying branch of structure, carries the load of satellite and engine, eight branch is shared between interior road-load lotus and from outside load
Beam 14 is supportted, plays the role of connection carrying, is also installed between each other for instrument and operation provides installation space, in shell section
Lower end be bearing 11, big jet pipe installs interface 12, small jet pipe installs interface 10 and gas cylinder installation position 13 and provides installation site,
Partial structurtes have carried out strengthening being used for increasing the stiffness characteristics around attitude control.
Wherein, in terms of vehicle instrument room bearing capacity, instrument room shell mechanism is using covering, stringer semi-monocoque construction shape
Formula, entirety alleviate the weight of structure while improving shell section carrying capacity；Centre is supported using trapezoidal backbar support structure
The load weight of engine and satellite, from outside branched structure will carry the load of rocket radome fairing, and interior road bifurcation load will be held
The load of engine and satellite is carried, such structure, which merges two-way load, to summarize, and is transferred in the substructure of rocket,
The stability of holding structure on the premise of bearing requirements are ensured.
Attitude control mounting structure design, instrument cabin structure have an important function that will provide installation space for attitude control and expire
The control of sufficient attitude control requires, and the installation interface of 20 attitude control jet pipes is shared in the instrument cabin structure, respectively along the axis of shell section
To, radial direction, tangential distribution.According to the high-precision requirement of posture control system, big rigidity, highly reliable installation site are provided for it,
High-strength aluminum alloy forging is used in this structure by attitude control nozzle carrier and instrument room shell segment structure stringer, covering, hypomere frame phase
Even, local stiffness characteristics are improved, and the tube-in-tube structure of attitude control jet pipe is used and is molded with titanium alloy 3D printing, is not only reduced
Structure takes weight, and improves the anti-thermal characteristics of entire shell section.
Instrument cable mounting structure design, structure of the present invention devise instrument installing plate in the upper end of supporting beam, i.e., rationally
The installation space that make use of rocket body structure narrow and small provides good load environment condition for accurate instrument and equipment again, the present invention
Instrument cabin structure, by medial fascicle and external shell connection rational in infrastructure, creative is set using support beam structure for instrument
It is standby that mounting platform and follow-up workers operating space are provided.In conclusion instrument room shell mechanism is using covering, half hard shell knot of stringer
Configuration formula, entirety alleviate the weight of structure while improving shell section carrying capacity；Centre uses trapezoidal backbar support structure
Support the load weight of engine and satellite, the stability of holding structure on the premise of bearing requirements are ensured.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
With within principle, any modifications, equivalent replacements and improvements are made should all be included in the protection scope of the present invention god.
Claims (7)
1. the instrument cabin structure of a kind of vehicle, including instrument room shell, which is characterized in that set on the outside of the instrument room shell
There is covering (1), the top and bottom of the instrument room shell are respectively equipped with upper end frame (2) and lower end frame (3), the upper end frame
(2) be respectively equipped with several upper blasting bolt boxes (5) and lower blasting bolt box (6) on the outside of outside and lower end frame (3), it is described on
Several hinge seats (8) are also associated on the outside of the frame of end, hinge hole, the instrument room are equipped on each described hinge seat (8)
The inside of shell is respectively equipped with interior road end frame (4) and Nei Lu lower ends frame (7), and the interior road end frame (4) passes through several supports
Beam (14) is connected with instrument room shell, and the upper end of the supporting beam is equipped with instrument installing plate, and Nei Lu lower ends frame (7) passes through purlin
Item (9) is connected with instrument room shell, and the lower end of the instrument room shell is equipped with several big jet pipe installation interfaces (12), small jet pipe
Interface (10), gas cylinder installation position (13) and bearing (11) are installed.
2. the instrument cabin structure of a kind of vehicle according to claim 1, which is characterized in that the supporting beam (14) is shared
Eight, be trapezoidal supporting beam.
A kind of 3. instrument cabin structure of vehicle according to claim 2, which is characterized in that each supporting beam (14)
On be equipped with several lightening holes.
A kind of 4. instrument cabin structure of vehicle according to claim 1, which is characterized in that big jet pipe installation interface (12)
20 are shared with small jet pipe installation interface (10), respectively along the axial direction of instrument room shell, radially and tangentially set.
A kind of 5. instrument cabin structure of vehicle according to claim 1, which is characterized in that the big jet pipe installation interface
(12) and small jet pipe installation interface (10) passes through stringer (9), covering (1) or the lower end of aluminum alloy forge piece and instrument room shell
Frame (3) is connected.
6. the instrument cabin structure of a kind of vehicle according to claim 5, which is characterized in that the big jet pipe installation connects
Mouth (12) and small jet pipe installation interface (10) are molded using titanium alloy 3D printing.
A kind of 7. instrument cabin structure of vehicle according to claim 1, which is characterized in that each described hinge seat
(8) include 2 hinge plates being separated by, and hinge hole is equipped on each hinge plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710210857.XA CN106864773B (en) | 2017-03-31 | 2017-03-31 | A kind of instrument cabin structure of vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710210857.XA CN106864773B (en) | 2017-03-31 | 2017-03-31 | A kind of instrument cabin structure of vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106864773A CN106864773A (en) | 2017-06-20 |
| CN106864773B true CN106864773B (en) | 2018-05-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710210857.XA Active CN106864773B (en) | 2017-03-31 | 2017-03-31 | A kind of instrument cabin structure of vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106864773B (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108725844B (en) * | 2018-06-26 | 2020-04-21 | 蓝箭航天空间科技股份有限公司 | Control cabin structure of space carrier |
| CN109050983A (en) * | 2018-08-31 | 2018-12-21 | 上海宇航系统工程研究所 | It is a kind of to support that big quality bilayer propulsion die is installed and the freighter of carrying promotes cabin structure |
| CN111023913A (en) * | 2019-12-27 | 2020-04-17 | 北京星际荣耀空间科技有限公司 | Carrier rocket final-stage structure |
| CN111846290B (en) * | 2020-08-06 | 2022-03-01 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| CN114659415B (en) * | 2022-03-01 | 2024-02-09 | 航天科工火箭技术有限公司 | Light cabin section structure of carrier |
| CN114940271A (en) * | 2022-03-08 | 2022-08-26 | 蓝箭航天空间科技股份有限公司 | Attitude control cabin of spacecraft and spacecraft |
| CN114812290A (en) * | 2022-05-24 | 2022-07-29 | 湖北航天技术研究院总体设计所 | Integrated structure of fairing and rocket adapter and carrier rocket |
| CN115854798B (en) * | 2022-12-28 | 2024-08-16 | 北京中科宇航技术有限公司 | Reverse-pushing small rocket flap separation direction verification tool |
| CN116428077A (en) * | 2023-03-16 | 2023-07-14 | 大连理工大学 | Main frame structure of carrier rocket engine with I-shaped section load beam |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP3979456B2 (en) * | 1998-07-24 | 2007-09-19 | 独立行政法人 宇宙航空研究開発機構 | Bundling control device for deployable frame structure |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN102303710A (en) * | 2011-06-08 | 2012-01-04 | 航天东方红卫星有限公司 | General propelling module for small satellites |
| CN104260903A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Propelling module structure with independent high-rail satellite platform function |
| CN206926839U (en) * | 2017-03-31 | 2018-01-26 | 北京蓝箭空间科技有限公司 | A kind of instrument cabin structure of vehicle |
-
2017
- 2017-03-31 CN CN201710210857.XA patent/CN106864773B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3979456B2 (en) * | 1998-07-24 | 2007-09-19 | 独立行政法人 宇宙航空研究開発機構 | Bundling control device for deployable frame structure |
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| CN102303710A (en) * | 2011-06-08 | 2012-01-04 | 航天东方红卫星有限公司 | General propelling module for small satellites |
| CN104260903A (en) * | 2014-09-16 | 2015-01-07 | 上海卫星工程研究所 | Propelling module structure with independent high-rail satellite platform function |
| CN206926839U (en) * | 2017-03-31 | 2018-01-26 | 北京蓝箭空间科技有限公司 | A kind of instrument cabin structure of vehicle |
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| Publication number | Publication date |
|---|---|
| CN106864773A (en) | 2017-06-20 |
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| PB01 | Publication | ||
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| TA01 | Transfer of patent application right |
Effective date of registration: 20170704 Address after: 100085, C, No. 28, No. two, information road, Beijing, Haidian District, 02B-492 Applicant after: BEIJING LANDSPACETECH Co.,Ltd. Address before: 100085, C, No. 28, No. two, information road, Beijing, Haidian District, 02B-492 Applicant before: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |
Effective date of registration: 20181024 Address after: 710077 East Building, four floor, aerospace science and technology, civil and integration innovation center, 32 United South Road, Xi'an, Shaanxi Patentee after: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. Address before: 100085 02B-492, information block C, seat 28 (two level), Haidian District, Beijing. Patentee before: BEIJING LANDSPACETECH Co.,Ltd. |
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| TR01 | Transfer of patent right |
Effective date of registration: 20240517 Address after: 100076 H1, AVIC International Plaza, No.13 Ronghua South Road, Daxing District, Beijing Economic and Technological Development Zone Patentee after: Blue Arrow Space Technology Co.,Ltd. Country or region after: China Address before: 710077 East Building, four floor, aerospace science and technology, civil and integration innovation center, 32 United South Road, Xi'an, Shaanxi Patentee before: SHAANXI LANDSPACE TECHNOLOGY Co.,Ltd. Country or region before: China |
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| TR01 | Transfer of patent right |